CN114542522A - Compressor blade damper and assembling method - Google Patents
Compressor blade damper and assembling method Download PDFInfo
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- CN114542522A CN114542522A CN202210158784.5A CN202210158784A CN114542522A CN 114542522 A CN114542522 A CN 114542522A CN 202210158784 A CN202210158784 A CN 202210158784A CN 114542522 A CN114542522 A CN 114542522A
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- 238000000034 method Methods 0.000 title claims abstract description 9
- 238000013016 damping Methods 0.000 claims description 110
- 230000000903 blocking effect Effects 0.000 claims description 19
- 239000000956 alloy Substances 0.000 claims description 4
- 239000011248 coating agent Substances 0.000 claims description 3
- 238000000576 coating method Methods 0.000 claims description 3
- 230000009467 reduction Effects 0.000 abstract description 12
- 230000000694 effects Effects 0.000 abstract description 7
- 238000010586 diagram Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 239000010432 diamond Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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- 238000007789 sealing Methods 0.000 description 1
- 230000007306 turnover Effects 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/62—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps
- F04D29/624—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a compressor blade damper and an assembling method, and relates to the technical field of gas turbines. The invention can solve the problems that the blade vibration reduction structure in the prior art limits the flow passage area, causes the weight increase of the blade body and the reduction of the aerodynamic performance, or is difficult to assemble, and the vibration reduction effect can not be adjusted.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a compressor blade damper and an assembling method.
Background
In the working process of a gas turbine compressor rotor blade, because the pneumatic pressure on the surface of the blade fluctuates along with time, the vibration on the blade can be excited, if an effective measure is not adopted to reduce the vibration level, the service life of the blade can be reduced, and even the blade can be broken due to overlarge vibration stress of the blade, so that the gas turbine is damaged.
In order to solve the problems, for the fan blades and the front stages of long blades of the compressor, in order to reduce the vibration of the blades, a vibration reduction boss is arranged on the blade body, and after the assembly is finished, the convex shoulders of the circumferential blades form a cylinder shape and are tightly propped against each other, so that the rigidity is enhanced, and the vibration stress of the blades is reduced. However, the damping shoulder also causes many problems, such as the reduction of the flow passage area by the damping shoulder, the reduction of the air flow, the additional aerodynamic loss, the increase of the weight of the blade body, and the increase of the centrifugal stress of the blade root. In order to deal with the problems brought by the damping convex shoulder, the shrouded blade is used for replacing the damping convex shoulder on the fan blade of some gas turbines, so that the leakage loss of the blade tip is reduced, the pneumatic performance is improved, but the weight of the blade tip is obviously increased, and the centrifugal load of the blade is larger. Meanwhile, the shrouded blade is complex in structure and difficult to assemble, and the shroud accounts for 10% or even higher of the weight of the whole blade. Therefore, the invention is needed to provide a damping structure with good vibration damping effect, simple structure and convenient installation.
Disclosure of Invention
The invention aims to provide a compressor blade damper and an assembly method, which can solve the problems that in the prior art, a blade vibration damping structure limits the area of a flow passage, so that the weight of a blade body is increased, the aerodynamic performance is reduced, or the assembly is difficult, the vibration damping effect cannot be adjusted, and the like. The technical scheme provided by the invention is as follows:
the compressor blade damper is a cylindrical body and is provided with an air inlet surface, an air exhaust surface, a first contact surface, a second contact surface and a bottom surface, the damper is an adjustable mass damper, the air inlet surface is positioned at one end of the damper, the air exhaust surface is positioned at the other end of the damper, the first contact surface and the second contact surface which are used for being in contact with a blade flange plate of a compressor moving blade are both positioned above the bottom surface and extend along the length direction of the damper, and the shape of the first contact surface is the same as or different from that of the second contact surface.
Optionally, the damper includes an intake damping block, at least one intermediate damping block, and an exhaust damping block, which are adjacently arranged in sequence, wherein the intake surface is located on the intake damping block, and the exhaust surface is located on the exhaust damping block.
Optionally, the middle damping block has a through hole, the intake damping block and the exhaust damping block have blind holes, a series rod passes through the through hole, a gap is formed between the series rod and the through hole, and the end of the series rod is respectively inserted into the blind hole of the intake damping block and the blind hole of the exhaust damping block.
Optionally, the end faces of the intake damping block, the middle damping block and the exhaust damping block are the same in shape or different in shape, the series rod is linear, and the intake damping block, the middle damping block and the exhaust damping block are assembled adjacently through the series rod.
In order to solve the technical problem, the invention further provides a compressor, which comprises an impeller, compressor moving blades and a compressor blade damper, wherein the compressor moving blades are mounted on the impeller, air blocking bosses are arranged on an air inlet side and an air outlet side of the impeller, an accommodating groove for assembling the damper is arranged on the impeller between the air inlet side and the air outlet side, an air inlet surface of the damper is close to a low-pressure side of the compressor, an air outlet surface of the damper is close to a high-pressure side of the compressor, a blade edge plate of the compressor moving blades comprises an air inlet baffle plate, an air outlet baffle plate and a middle section contact surface between the air inlet baffle plate and the air outlet baffle plate, the middle section contact surface is located above the damper, and the middle section contact surface is used for contacting with the first contact surface or the second contact surface.
Optionally, the air blocking boss on the air inlet side is adjacent to the air inlet baffle, the air blocking boss on the air outlet side is adjacent to the air outlet baffle, and the damper is assembled in a cavity surrounded by the blade edge plate of the adjacent compressor moving blade and the impeller. The air inlet baffle is positioned above the air blocking boss at the air inlet side and is flush with the air blocking boss, and the exhaust baffle is positioned above the air blocking boss at the exhaust side and is flush with the air blocking boss.
Optionally, the distance between the contact surface of the middle section and the bottom surface of the accommodating groove is larger than the height of the damper.
Optionally, the inlet baffle is adapted to contact the inlet face during operation of the gas turbine, and the outlet baffle is adapted to contact the outlet face during operation of the gas turbine.
Optionally, the damper is made of a high-temperature alloy material, and a wear-resistant coating is coated on the outer surface of the damper.
Optionally, the width of the accommodating groove is equal to or slightly greater than the width of the bottom surface of the damper.
The invention also provides a gas turbine which comprises the compressor blade damper or the compressor.
In order to solve the technical problem, the invention further provides a compressor assembly method, which comprises the steps of installing the compressor blade damper in an accommodating groove on the impeller, and then installing the compressor moving blades in a blade root groove of the impeller along the axial direction of the impeller.
Compared with the prior art, the technical scheme provided by the invention has the following beneficial effects:
(1) on the basis of fully researching the vibration reduction damping structure of the compressor moving blade, the damping structure is designed between the blade flange plate and the wheel rim, so that the vibration of the blade can be effectively reduced by establishing dry friction damping, and the vibration performance of the blade is improved. The invention has certain significance for ensuring the safe and stable operation of the unit. In addition, the damping structure has various modifications, so that the vibration of the blade can be effectively reduced;
(2) when the gas turbine unit is in operation, the blade damper is in contact with the underside of the blade edge plate under the action of centrifugal force. When the blade is excited by airflow force, dry friction damping is formed among the blade damper, the blade edge plate, the adjacent damping blocks and between the damping blocks and the serial rods, so that the aim of vibration reduction is fulfilled, and meanwhile, the quality of the damper is adjusted to ensure the best vibration reduction capability by increasing or decreasing the number of the middle damping blocks or replacing the middle damping blocks with different qualities;
(3) the invention has simple structure and convenient assembly and disassembly, and the damper is an adjustable mass damper, which can effectively increase the damping of the blade and reduce the vibration of the blade, thereby ensuring the reliability of the unit.
Drawings
Fig. 1 is a schematic view of a partial structure of a compressor according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a damper according to an embodiment of the present invention;
FIG. 3 is a schematic view of a damper assembly according to an embodiment of the present invention;
FIG. 4 is a schematic structural diagram of a compressor moving blade according to an embodiment of the present invention;
fig. 5 is a schematic structural diagram of an impeller of a compressor according to an embodiment of the present invention;
FIG. 6 is an assembled cross-sectional view of a damper according to embodiment 1 of the invention;
FIG. 7 is an assembled cross-sectional view of a damper according to embodiment 2 of the invention;
FIG. 8 is an assembled cross-sectional view of a damper according to embodiment 3 of the invention;
FIG. 9 is an assembled cross-sectional view of a damper according to embodiment 4 of the invention;
fig. 10 is an assembled cross-sectional view of a damper according to embodiment 5 of the present invention.
Reference numerals: 1. an impeller; 2. moving blades of a gas compressor; 3. a damper; 4. an intake damping block; 5. a containing groove; 6. a blade platform; 7. a leaf root groove; 8. an exhaust damping block; 9. an air inlet surface; 10. an exhaust surface; 11. a first contact surface; 12. a second contact surface; 13. a bottom surface; 14. a through hole; 15. a series rod; 16. a gas blocking boss; 17. an intake baffle; 18. a middle section contact surface; 19. an exhaust baffle; 20. and a middle damping block.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention and are not to be construed as limiting the present invention.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as being fixedly connected, integrally connected, or detachably connected; either mechanically or electrically, or internally communicating two elements; they may be directly connected or indirectly connected through an intermediate, and a person of ordinary skill in the art can understand the specific meaning of the terms according to the specific situation.
As shown in fig. 2 and 3, the damper 3 includes a plurality of damping blocks, the damper 3 is a cylindrical body, and has an air inlet surface 9, an air outlet surface 10, a first contact surface 11, a second contact surface 12, and a bottom surface 13, the damper is an adjustable mass damper, the air inlet surface 9 is located at one end of the damper 3, the air outlet surface 10 is located at the other end of the damper 3, the first contact surface 11 and the second contact surface 12 for contacting with the blade edge plate 6 of the compressor moving blade 2 are both located above the bottom surface 13 and extend along the length direction of the damper 3, and the shapes of the first contact surface 11 and the second contact surface 12 are the same or different. The damper 3 comprises an air inlet damping block 4, at least one middle damping block 20 and an air outlet damping block 8 which are sequentially and adjacently arranged, wherein an air inlet surface 9 is positioned on the air inlet damping block 4, and an air outlet surface 10 is positioned on the air outlet damping block 8. The middle damping block 20 is provided with a through hole 14, the air inlet damping block 4 and the air outlet damping block 8 are provided with blind holes, the serial rod 15 penetrates through the through hole 14, a gap is reserved between the serial rod 15 and the through hole 14, and the end parts of the serial rod 15 are respectively inserted into the blind hole of the air inlet damping block 4 and the blind hole of the air outlet damping block 8. The adjacent damping blocks are connected together through the serial rods 15, and the damping blocks are in clearance fit with the serial rods 15. The masses of the middle damping blocks 20 can be the same or different, and the middle damping blocks 20 can be selected to be combined according to the vibration reduction requirement. The air inlet damping block 4, the middle damping block 20 and the exhaust damping block 8 are made of high-temperature alloy and are made of the same material. The intake, intermediate and exhaust damping masses 4, 20, 8 may vary in size. The intake damper mass 4, the intermediate damper mass 20 and/or the exhaust damper mass 8 have a longitudinal cross-sectional width greater than their height.
In another embodiment, the end surfaces of the intake damping block 4, the intermediate damping block 20 and the exhaust damping block 8 are all the same in shape, the end surfaces may be flat surfaces, when a plurality of intermediate damping blocks are adjacently installed, the intermediate damping blocks are in close contact, the friction force is uniform, the series rod 15 is linear, the series rod 15 is preferably a cylindrical rod, the surface of the series rod 15 is flat and smooth, the assembly is more convenient, the damping blocks are allowed to rotate on the series rod 15, the vibration absorption is facilitated, and the intake damping block 4, the intermediate damping block 20 and the exhaust damping block 8 are adjacently assembled through the series rod 15. The material of the series rod 15 is preferably the same as that of the intake damping block 4, the intermediate damping block 20 and the exhaust damping block 8; the longitudinal section shapes of the air inlet damping block 4, the middle damping block 20 and the exhaust damping block 8 can be processed into a semicircle shape, a roof shape, a fan shape, a dumbbell shape or an arch shape, and the longitudinal section shapes of the air inlet damping block 4, the middle damping block 20 and the exhaust damping block 8 are the same or different.
In other embodiments, the end surface shapes of the intake damper block 4, the intermediate damper block 20, and the exhaust damper block 8 are all different.
In other embodiments, the shape and position of the first contact surface 11 and the second contact surface 12 are mirror images of each other, e.g. are inclined planes with the same angle to the horizontal plane, showing the same sloping sides in the cross-section of the damping mass.
In other embodiments, when the serial rod is a cylindrical rod, circular grooves and circular flanges which are matched with each other can be respectively arranged on the end surfaces of the air inlet damping block, the middle damping block and the exhaust damping block, one of the adjacent corresponding end surfaces is a circular groove, the other end surface is a circular flange, and the circle centers of the circular grooves and the circular flanges are coincided with the axis of the cylindrical rod, so that the adjustability of the vibration damping effect is better; the two end faces of the single middle damping block can be a face with a circular groove or a circular flange, and the other face is a flat surface. In order to make the friction stress more uniform, anti-skid patterns can be arranged on the end surfaces of the air inlet damping block, the middle damping block and the exhaust damping block, or anti-skid stripes can be arranged on the surfaces of the circular groove and the circular flange, and the anti-skid patterns can be used as an adjusting means of the damping effect of the damper.
In other embodiments, the tandem bar 15 is square or diamond shaped or oval or rounded rectangular in cross-section.
In other embodiments, the serial rod 15 is an elongated threaded rod, and the serial rod 15 is in threaded connection with the air damping block, the middle damping block 20 and the exhaust damping block 8, so that the position of the damping blocks on the serial rod 15 and the distance between the damping blocks are maintained.
The embodiment of the invention also provides a compressor, as shown in fig. 1 to 5, which comprises an impeller 1, compressor moving blades 2 and a compressor blade damper 3, wherein the compressor moving blades 2 are installed on the impeller 1, air blocking bosses 16 are arranged on the air inlet side and the air outlet side of the impeller 1, the air blocking bosses 16 are integrally formed with the impeller 1, an accommodating groove 5 for assembling the damper 3 is arranged on the impeller 1 between the air inlet side and the air outlet side, the accommodating groove 5 is preferably a rectangular accommodating groove 5, the width of the bottom surface 13 of the compressor blade damper 3 is preferably equal to the width of the rectangular accommodating groove 5, and the longitudinal section of the rectangular accommodating groove can be an inverted trapezoid with a large opening at the top and a small opening at the bottom so as to accommodate the damper; the air inlet surface 9 of the damper 3 is close to the low-pressure side of the compressor, the air outlet surface 10 of the damper 3 is close to the high-pressure side of the compressor, the blade edge plate 6 of the compressor moving blade 2 comprises an air inlet baffle plate 17, an air outlet baffle plate 19 and a middle section contact surface 18 located between the air inlet baffle plate 17 and the air outlet baffle plate 19, the middle section contact surface 18 is located on the lower side of the blade edge plate 6, the middle section contact surface 18 is located above the damper 3, and the middle section contact surface 18 is used for being in contact with the first contact surface 11 or the second contact surface 12. The mid-section contact surface 18 is beveled, flat or radiused. When the damper is installed, the damper 3 is arranged in the rectangular accommodating groove 5 of the impeller 1, and then the compressor moving blades 2 are axially slid into the blade root grooves 7 to be flush with the air blocking bosses 16; when the unit is in operation, under the action of centrifugal force, the first contact surface 11 or the second contact surface 12 of the damper 3 is in contact with the middle section contact surface 18; when the compressor moving blade 2 is excited by airflow force, dry friction damping is formed between the damper 3 and the compressor moving blade 2, between adjacent damping blocks and between the damping blocks and the series rod 15, so that the aim of vibration reduction is fulfilled.
The inlet baffle 17 is intended to be in contact with the inlet face 9 during operation of the gas turbine, and the outlet baffle 19 is intended to be in contact with the outlet face 10 during operation of the gas turbine. The air blocking boss 16 at the air inlet side is adjacent to the air inlet baffle 17, the air blocking boss 16 at the air exhaust side is adjacent to the air exhaust baffle 19, and the damper 3 is assembled in a cavity surrounded by the blade edge plate 6 of the adjacent compressor moving blade 2 and the impeller 1; in order to facilitate the assembly of the blades, installation gaps are reserved among the air blocking boss 16, the air inlet baffle 17 and the exhaust baffle 19. The air inlet baffle 17 is positioned above the air inlet side air baffle boss 16 and is flush with the air baffle boss 16, and the exhaust baffle 19 is positioned above the exhaust side air baffle boss 16 and is flush with the air baffle boss 16; the air blocking boss 16, the air inlet baffle 17 of the blade edge plate 6 and the exhaust baffle 19 form a sealing structure, high-temperature and high-pressure gas can be prevented from flowing into the cavity assembled with the damper 3, the maximum width inside the cavity is larger than the maximum height inside the cavity, the width of the cross section of the damper or the damping block is larger than the height of the damper or the damping block, and the height of the inner height of the cavity and the height of the damper are set to ensure that the damper or the damping block cannot turn over by more than 90 degrees in the cavity. The distance between the middle section contact surface and the bottom surface of the containing groove is larger than the height of the damper, the damper is allowed to move up and down in the cavity, the containing groove can be used for placing the damper when the blades are assembled, the damper does not influence the assembly of the blades, the follow-up effect of the damper is achieved when the assembly is convenient, the damper can move along with the change of the rotating speed of the compressor blades, and the vibration reduction effect with certain self-adaptability can be achieved.
The damper 3 is made of high-temperature alloy materials, the outer surface of the damper 3 is coated with a wear-resistant coating, and the air inlet damping block 4, the middle damping block 20 and the exhaust damping block 8 are made of the same material.
In other embodiments, the width of the receiving groove is equal to or slightly greater than the width of the bottom surface of the damper.
The embodiment of the invention also provides a gas turbine which comprises the compressor blade damper or the compressor.
The embodiment of the invention also provides a compressor assembly method, which comprises the steps of installing the compressor blade damper 3 in the accommodating groove 5 on the impeller 1, and then installing the compressor moving blades 2 in the blade root grooves 7 of the impeller 1 along the axial direction of the impeller 1 until the air inlet baffle 17 and the air exhaust baffle 19 of the compressor moving blades 2 are flush with the air blocking boss 16 of the impeller 1. When the gas turbine is in a shutdown state, the bottom surface 13 of the compressor blade damper 3 is in contact with the bottom surface of the accommodating groove 5; when the gas turbine is in an operating state, the first contact surface 11 and the second contact surface 12 of the compressor blade damper 3 are abutted against the middle section contact surface 18 of the blade flange plate 6, and when the compressor moving blade 2 is excited by airflow force, the compressor blade damper 3 and the blade flange plate 6 rub to reduce the vibration of the compressor moving blade 2.
Example 1
As shown in fig. 6, the cross-sectional shape of the compressor blade damper 3 may be made into a semicircular shape, the first contact surface 11 and the second contact surface 12 are both arc surfaces, and the bottom surface 13 is a plane and has a width equal to or slightly smaller than the width of the accommodating groove 5. The middle section contact surface 18 is in the shape of an arc surface, and the radius of the arc surface is equal to the semi-circle radius of the damper 3.
Example 2
As shown in fig. 7, the cross-sectional shape of the compressor blade damper 3 may be made into a fan shape, the first contact surface 11 is an inclined surface, the second contact surface 12 is an arc surface, and the bottom surface 13 is a plane and has a width equal to or slightly smaller than the width of the accommodating groove 5. The intermediate section contact surface 18, which contacts the first contact surface 11, is shaped as an inclined surface, and the length and width of the inclined surfaces are equal. The middle section contact surface 18 in contact with the second contact surface 12 is shaped as an arc surface with a radius equal to the radius of the arc surface of the second contact surface 12.
Example 3
As shown in fig. 8, the compressor blade damper 3 may be formed in a roof shape in cross section, the first contact surface 11 is an inclined surface, the second contact surface 12 is an inclined surface, and the width of the bottom surface 13 is equal to or slightly smaller than the width of the accommodating groove 5. The intermediate section contact surface 18 is shaped as an inclined surface with an angle of inclination equal to the angle of inclination of the first contact surface 11.
Example 4
As shown in fig. 9, the cross-sectional shape of the compressor blade damper 3 may be made into a dumbbell shape, the first contact surface 11 is an arc, the second contact surface 12 is an arc, and the width of the bottom surface 13 is equal to or slightly smaller than the width of the accommodating groove 5. The mid-section contact surface 18 of the blade platform 6 used in conjunction with the dumbbell damper 3 is planar.
Example 5
As shown in fig. 10, the compressor blade damper 3 may be formed in an arch shape in cross section, the first contact surface 11 is an arc surface, the second contact surface 12 is an arc surface, and the width of the bottom surface 13 is equal to or slightly smaller than the width of the accommodating groove 5. The middle section contact surface 18 matched with the arched damper 3 is in the shape of an arc surface, and the radius of the arc surface is equal to that of the arc surface of the first contact surface 11.
The present invention and its embodiments have been described above schematically, without limitation, and what is shown in the drawings is only one of the embodiments of the present invention, and the actual structure is not limited thereto. Therefore, if the person skilled in the art receives the teaching, without departing from the spirit of the invention, the person skilled in the art shall not inventively design the similar structural modes and embodiments to the technical solution, but shall fall within the scope of the invention.
Claims (10)
1. The compressor blade damper is characterized in that the damper is a cylindrical body and is provided with an air inlet surface, an air exhaust surface, a first contact surface, a second contact surface and a bottom surface, the damper is an adjustable mass damper, the air inlet surface is positioned at one end of the damper, the air exhaust surface is positioned at the other end of the damper, the first contact surface and the second contact surface which are used for being in contact with a blade flange plate of a compressor moving blade are both positioned above the bottom surface and extend along the length direction of the damper, and the shape of the first contact surface is the same as or different from that of the second contact surface.
2. The compressor blade damper of claim 1, comprising an intake damping mass, at least one intermediate damping mass, and an exhaust damping mass arranged adjacent to one another in sequence, the intake face being on the intake damping mass and the exhaust face being on the exhaust damping mass.
3. The compressor blade damper of claim 2, said intermediate damping block having a through hole, said intake damping block and said exhaust damping block having blind holes, said through hole having a series rod passing therethrough, said series rod having a gap with said through hole, ends of said series rod being inserted into said blind holes of said intake damping block and said blind holes of said exhaust damping block, respectively.
4. The compressor blade damper as claimed in claim 3 wherein the inlet, intermediate and exhaust damping blocks have end faces of the same or different shape, the series rod is linear, and the inlet, intermediate and exhaust damping blocks are assembled adjacent to each other via the series rod.
5. A compressor characterized by comprising an impeller, compressor moving blades mounted on the impeller, and a compressor blade damper according to any one of claims 1 to 4, air blocking bosses are arranged on the air inlet side and the air outlet side of the impeller, an accommodating groove for assembling the damper is arranged on the impeller between the air inlet side and the air outlet side, the air inlet surface of the damper is close to the low-pressure side of the compressor, the air outlet surface of the damper is close to the high-pressure side of the compressor, the blade edge plate of the moving blade of the compressor comprises an air inlet baffle plate, an air exhaust baffle plate and a middle section contact surface positioned between the air inlet baffle plate and the air exhaust baffle plate, the middle section contact surface is located above the damper and is used for contacting with the first contact surface or the second contact surface.
6. The compressor of claim 5, wherein the air blocking boss on the air inlet side is adjacent to the air inlet baffle, the air blocking boss on the air outlet side is adjacent to the air outlet baffle, and the damper is fitted in a cavity surrounded by the blade edge plate of the adjacent compressor moving blades and the impeller.
7. The compressor of claim 5 or 6, wherein the distance between the contact surface of the middle section and the bottom surface of the accommodating groove is greater than the height of the damper.
8. The compressor of claim 7, wherein the damper is made of a high-temperature alloy material, and the outer surface of the damper is coated with a wear-resistant coating.
9. Gas turbine engine, characterized in that it comprises a compressor blade damper according to any one of claims 1 to 4 or a compressor according to any one of claims 5 to 8.
10. A compressor assembling method, characterized by comprising mounting the compressor blade damper according to any one of claims 1 to 4 in a containing groove on an impeller, and then mounting the compressor moving blade according to any one of claims 5 to 8 in a root groove of the impeller in an axial direction of the impeller.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210158784.5A CN114542522A (en) | 2022-02-21 | 2022-02-21 | Compressor blade damper and assembling method |
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| CN202210158784.5A CN114542522A (en) | 2022-02-21 | 2022-02-21 | Compressor blade damper and assembling method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116538151A (en) * | 2023-05-18 | 2023-08-04 | 中国船舶集团有限公司第七〇三研究所 | Micro-texture-based compressor damping blade structure |
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| CN206928974U (en) * | 2017-07-19 | 2018-01-26 | 中国航发商用航空发动机有限责任公司 | blade damper, turbine and aero-engine |
| CN108474260A (en) * | 2016-01-12 | 2018-08-31 | 西门子股份公司 | Flexible damper for turbine bucket |
| US20210172326A1 (en) * | 2019-12-10 | 2021-06-10 | General Electric Company | Damper stacks for turbomachine rotor blades |
| KR20220012472A (en) * | 2020-07-22 | 2022-02-04 | 두산중공업 주식회사 | rotor and turbo-machine comprising the same |
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2022
- 2022-02-21 CN CN202210158784.5A patent/CN114542522A/en active Pending
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| JP2000008804A (en) * | 1998-06-25 | 2000-01-11 | Ishikawajima Harima Heavy Ind Co Ltd | Turbine rotor blade vibration control device of gas turbine |
| US20100034657A1 (en) * | 2007-05-25 | 2010-02-11 | Rolls-Royce Plc | Vibration damper assembly |
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| CN103850729A (en) * | 2012-11-28 | 2014-06-11 | 通用电气公司 | System for damping vibrations in turbine |
| CN108474260A (en) * | 2016-01-12 | 2018-08-31 | 西门子股份公司 | Flexible damper for turbine bucket |
| CN205936703U (en) * | 2016-08-12 | 2017-02-08 | 中国航空工业集团公司沈阳发动机设计研究所 | High pressure turbine rotor blade damping structure of obturaging |
| CN206928974U (en) * | 2017-07-19 | 2018-01-26 | 中国航发商用航空发动机有限责任公司 | blade damper, turbine and aero-engine |
| US20210172326A1 (en) * | 2019-12-10 | 2021-06-10 | General Electric Company | Damper stacks for turbomachine rotor blades |
| KR20220012472A (en) * | 2020-07-22 | 2022-02-04 | 두산중공업 주식회사 | rotor and turbo-machine comprising the same |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116538151A (en) * | 2023-05-18 | 2023-08-04 | 中国船舶集团有限公司第七〇三研究所 | Micro-texture-based compressor damping blade structure |
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Address after: 310000 Building 1, No. 608, Kangxin Road, Linping District, Hangzhou, Zhejiang Applicant after: Hangzhou Turbine Power Group Co.,Ltd. Address before: 310000 Building 1, No. 608, Kangxin Road, economic and Technological Development Zone, Yuhang District, Hangzhou City, Zhejiang Province Applicant before: HANGZHOU STEAM TURBINE Co.,Ltd. |